5362 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on January 

6, 2017. 

Melvin Johnson, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2017–00502 Filed 1–17–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0831; Directorate 

Identifier 2014–NM–061–AD; Amendment 

39–18778; AD 2017–01–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318 and A319 series 

airplanes, Model A320–211, –212, –214, 

–231, –232, and –233 airplanes, and 

Model A321 series airplanes. This AD 

was prompted by a report of a rupture 

of a main landing gear (MLG) sliding 

tube axle. This AD requires 

identification of the part number and 

serial number of the MLG sliding tubes; 

inspection of affected chromium plates 

and sliding tube axles for damage; and 

replacement of the sliding tube if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 22, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 22, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0831. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0831; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Airbus Model 

A318 and A319 series airplanes, Model 

A320–211, –212, –214, –231, –232, and 

–233 airplanes, and Model A321 series 

airplanes. The SNPRM published in the 

Federal Register on June 28, 2016 (81 

FR 41886) (‘‘the SNPRM’’). We preceded 

the SNPRM with a notice of proposed 

rulemaking (NPRM) that published in 

the Federal Register on April 24, 2015 

(80 FR 22939) (‘‘the NPRM’’). The 

NPRM proposed to require an 

inspection to identify the part number 

and serial number of the MLG sliding 

tubes installed on the airplane; an 

inspection of the axle on certain MLG 

sliding tubes for damage; and 

replacement of the sliding tube if 

necessary. The NPRM was prompted by 

a report of a rupture of a MLG sliding 

tube axle. The SNPRM proposed to 

remove certain service information that 

does not adequately address the 

identified unsafe condition and revise 

the compliance method. We are issuing 

this AD to detect and correct cracks in 

the axle and (partial) detachment of the 

axle and wheel from the sliding tube, 

which could result in failure of an MLG. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0058, dated March 11, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A318 and A319 series airplanes, 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes, and Model 

A321 series airplanes. The MCAI states: 

A main landing gear (MLG) sliding tube 

axle rupture occurred in service. 

Investigation of the affected part showed that 

this failure was due to an abnormal grinding 

operation during overhaul by a certain 

maintenance and repair organization located 

in Singapore. A population of MLG sliding 

tubes was subsequently identified whose 

axles may have been subject to this grinding 

operation, which may have resulted in areas 

of residual stress on the axles on the MLG 

sliding tubes. In addition, the MSN 

[manufacturer serial number] of the 

aeroplanes which are known to have had the 

affected parts installed have been identified. 

This condition, if not detected and 

corrected, could lead to cracks in the axle 

and (partial) detachment of axle and wheel 

from the sliding tube, possibly resulting in 

failure of a MLG with consequent damage to 

the aeroplane and injury to occupants. 

To address this potential unsafe condition, 

Messier-Bugatti-Dowty, the MLG gear 

manufacturer, issued Service Bulletin (SB) 

200–32–313 and SB 201–32–62 [both dated 

February 25, 2013], providing inspection 

instructions and criteria for removal from 

service of the affected MLG sliding tubes. 

For the reasons described above, this 

[EASA] AD requires a one-time Special 

Detailed Inspection (SDI) of the axle on the 

affected MLG sliding tubes and, depending 

on findings, replacement of the MLG sliding 

tube. 

The SDI includes a detailed visual 

inspection of the chromium plate for 

damage, and a Barkhausen noise 

inspection of the sliding tube axles for 

damage. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0831. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations 5363 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–32–1416, including Appendix 01, 

dated March 10, 2014. This service 

information describes procedures for 

inspecting MLG axles and brake flanges 

by doing a detailed visual inspection of 

the chromium plates for damage, a 

Barkhausen noise inspection of the 

sliding tube axles for damage, and 

replacement of affected parts if 

necessary. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 3 

airplanes of U.S. registry. 

We also estimate that it would take 

about 18 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $4,590, or $1,530 per 

product. 

In addition, we estimate that any 

necessary on-condition actions will take 

about 3 work-hours, for a cost of $255 

per product. We have received no 

definitive data that would enable us to 

provide part cost estimates for the oncondition actions specified in this AD. 

We have no way of determining the 

number of aircraft that might need these 

actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2017–01–11 Airbus: Amendment 39–18778; 

Docket No. FAA–2015–0831; Directorate 

Identifier 2014–NM–061–AD. 

(a) Effective Date 

This AD is effective February 22, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of a 

rupture of a main landing gear (MLG) sliding 

tube axle. We are issuing this AD to detect 

and correct cracks in the axle and (partial) 

detachment of the axle and wheel from the 

sliding tube, which could result in failure of 

an MLG. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) MLG Sliding Tube Part Number and 

Serial Number Identification 

Within 3 months after the effective date of 

this AD: Do an inspection to identify the part 

number and serial number of the MLG 

sliding tubes installed on the airplane. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number and serial number of the MLG 

sliding tubes can be conclusively determined 

from that review. 

(h) Identification of Airplanes Not Affected 

by the Requirements of Paragraph (i) of this 

AD 

An airplane with a manufacturer serial 

number (MSN) not listed in figure 1 to 

paragraph (h) of this AD is not affected by the 

requirements of paragraph (i) of this AD, 

provided it can be determined that no MLG 

sliding tube having a part number and serial 

number listed in table 1 to paragraphs (h), (i), 

(k)(1), (k)(2), (l)(1), and (l)(2) of this AD has 

been installed on that airplane since first 

flight of the airplane. 

FIGURE 1 TO PARAGRAPH (H) OF THIS AD 

Affected Airplanes Listed by MSN 

0179 0214 0296 0412 0558 0604 

0607 0668 0704 0720 0726 0731 

0754 0771 0799 0828 0841 0855 

0909 0914 0925 0939 0986 1028 

1030 1041 1070 1083 1093 1098 

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5364 Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations 

FIGURE 1 TO PARAGRAPH (H) OF THIS AD—Continued 

1108 1148 1294 1356 2713 2831 

TABLE 1 TO PARAGRAPHS (h), (i), 

(k)(1), (k)(2), (l)(1), AND (l)(2) OF

THIS AD—AFFECTED MLG SLIDING

TUBES

Part No. Serial No. 

201160302 ............................ 78B 

201160302 ............................ 1016B11 

201160302 ............................ 1144B 

201371302 ............................ B4493 

201371302 ............................ B4513 

201371302 ............................ SS4359 

201371302 ............................ B4530 

201371302 ............................ B4517 

201371302 ............................ B4568 

201371302 ............................ B4498 

201371302 ............................ 4490B 

201371302 ............................ B202–4598 

201371302 ............................ B165–4623 

201371302 ............................ B244–4766 

201371302 ............................ B267–4794 

201371302 ............................ B272–4813 

201160302 ............................ 1108B 

201371304 ............................ B041–4871 

201371304 ............................ B045–4869 

201371304 ............................ B001–4781 

201371304 ............................ B051–4892 

201371304 ............................ B110–1952 

201371304 ............................ B054–4891 

201371304 ............................ B063–4921 

201371304 ............................ B071–4911 

201371304 ............................ B071–4917 

201371304 ............................ B080–1933 

201371304 ............................ B117–5010 

201371304 ............................ B120–4989 

201371304 ............................ B132–2023 

201371304 ............................ B114–1956 

201371304 ............................ B208–2009 

201371304 ............................ B133–1947 

201371304 ............................ B154–5037 

201371304 ............................ B89 4952 

201371304 ............................ B129–1964 

201371304 ............................ B227–2010 

201371304 ............................ B170–5031 

201371304 ............................ B182–5047 

201371304 ............................ B239–2053 

201371304 ............................ B1401–2856 

201371304 ............................ B1813–3142 

201371304 ............................ B116–5004 

201522353 ............................ B011–149 

201522350 ............................ B014–25 

201522350 ............................ B019–56 

201522350 ............................ B019–57 

201522350 ............................ B021–69 

201522350 ............................ B022–60 

201522353 ............................ B03–111 

201522353 ............................ B03–110 

201522353 ............................ B112–317 

201522353 ............................ B174–351 

201522353 ............................ B179–392 

201383350 ............................ 4377B 

201383350 ............................ 4393B 

201383350 ............................ B1831 

201383350 ............................ B1832 

201383350 ............................ SS4355B 

201383350 ............................ SS4400B 

(i) Inspections 

For each MLG sliding tube identified as 

required by paragraph (g) of this AD, having 

a part number and serial number listed in 

table 1 to paragraphs (h), (i), (k)(1), (k)(2), 

(l)(1), and (l)(2) of this AD: Within 3 months 

after the effective date of this AD, inspect 

affected MLG axles and brake flanges by 

doing a detailed visual inspection of the 

chromium plates for damage, and a 

Barkhausen noise inspection of the sliding 

tube axles for damage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014. For 

Model A318 series airplanes, use the 

procedures specified for Model A319 series 

airplanes in Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. 

(j) Corrective Action 

If, during any inspection required by 

paragraph (i) of this AD, any damage is 

detected: Before further flight, replace the 

MLG sliding tube with a serviceable tube, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. For Model A318 series 

airplanes, use the procedures specified for 

Model A319 series airplanes in Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014. 

(k) Definition of Serviceable Sliding Tube 

For the purpose of this AD, a serviceable 

sliding tube is defined as a sliding tube that 

meets the criterion in either paragraph (k)(1) 

or (k)(2) of this AD. 

(1) A sliding tube having a part number 

and serial number not listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of this AD. 

(2) A sliding tube having a part number 

and serial number listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of this AD that has passed the 

inspections required by paragraph (i) of this 

AD. 

(l) Parts Installation Prohibitions 

(1) For airplanes that have an MLG sliding 

tube installed that has a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD: After an airplane is returned to service 

following accomplishment of the actions 

required by paragraphs (g), (h), and (i) of this 

AD, no person may install on any airplane an 

MLG sliding tube having a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD unless that sliding tube has passed the 

inspection required by paragraph (i) of this 

AD. 

(2) For airplanes that, as of the effective 

date of this AD, do not have an MLG sliding 

tube installed that has a part number and 

serial number listed in table 1 to paragraphs 

(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this 

AD: No person may install on any airplane 

an MLG sliding tube having a part number 

and serial number listed in table 1 to 

paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 

(l)(2) of this AD unless that sliding tube has 

passed the inspection required by paragraph 

(i) of this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9–ANM–116– 

AMOC–REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(3) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(n) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the MLG remains extended 

throughout the flight. 

(o) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations 5365 

Airworthiness Directive 2014–0058, dated 

March 11, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–0831. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–32–1416, 

including Appendix 01, dated March 10, 

2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

4, 2017. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2017–00408 Filed 1–17–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9058; Directorate 

Identifier 2016–NM–024–AD; Amendment 

39–18771; AD 2017–01–04] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F28 Mark 

0100 airplanes. This AD was prompted 

by an analysis which determined that, 

for certain areas of the fuselage, the 

current threshold of an Airworthiness 

Limitations Section inspection is 

insufficient to detect early crack 

development. This AD requires one time 

high and low frequency eddy current 

inspections of the affected fuselage skin 

for cracks, and repair if necessary. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 22, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 22, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone: 

+31 (0)88–6280–350; fax: +31 (0)88– 

6280–111; email: technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

9058. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

9058; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425 227 1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Fokker Services B.V. 

Model F28 Mark 0100 airplanes. The 

NPRM published in the Federal 

Register on September 8, 2016 (81 FR 

62029) (‘‘the NPRM’’). The NPRM was 

prompted by an analysis which 

determined that, for certain areas of the 

fuselage, the current threshold of an 

Airworthiness Limitations Section 

inspection is insufficient to detect early 

crack development. The NPRM 

proposed to require one time high and 

low frequency eddy current inspections 

of the affected fuselage skin for cracks, 

and repair if necessary. We are issuing 

this AD to detect and correct cracks in 

the fuselage skin; such cracking could 

result in reduced structural integrity of 

the fuselage. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive Airworthiness Directive 2016– 

0029R1, dated November 17, 2016 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Fokker Services 

B.V. Model F28 Mark 0100 airplanes. 

The MCAI states: 

A complementary fatigue and damage 

tolerance analysis was accomplished by the 

design approval holder on the traffic 

collision avoidance system (TCAS) antenna 

installation on the top of the fuselage 

between station (STA) 6805 and STA7305. 

Based on the results, it was determined that 

for the affected area, the current 58 000 flight 

cycles (FC) threshold of Airworthiness 

Limitations Section (ALS) inspection task 

533001–00–20 and 533028–00–20 (special 

detailed inspection of longitudinal lap joints) 

is insufficient to timely detect possible crack 

development. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the fuselage in this area. 

To address this potential unsafe condition, 

Fokker Services published Service Bulletin 

(SB) SBF100–53–130 to provide inspection 

instructions. 

Consequently, EASA issued AD 2016–0029 

to require a one-time inspection of the 

fuselage skin around the largest TCAS 

antenna external doubler and of the 

longitudinal lap joint at stringer (STR) 37 

between fuselage STA6805 and STA7305. 

Since that [EASA] AD was issued, it was 

discovered that another ALS inspection task, 

533028–00–20, is also related to this subject. 

This [EASA] AD is revised to clarify that the 

inspection threshold of both ALS inspection 

tasks has been re-assessed. It is expected that 

a repetitive inspection task will be included 

in the ALS, which will cover only the area 

close to the TCAS antenna installation. For 

the remainder of the affected lap joint, no 

change is anticipated and this will therefore 

continue to be inspected in accordance with 

the existing ALS tasks. 

This [EASA] AD is still considered to be 

an interim action and further [EASA] AD 

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